CN105781625A - Fixture and method for installing turbine buckets - Google Patents
Fixture and method for installing turbine buckets Download PDFInfo
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- CN105781625A CN105781625A CN201610017156.XA CN201610017156A CN105781625A CN 105781625 A CN105781625 A CN 105781625A CN 201610017156 A CN201610017156 A CN 201610017156A CN 105781625 A CN105781625 A CN 105781625A
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- Prior art keywords
- rotor blade
- turbine rotor
- dovetail groove
- keeper
- wheel
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- 238000012546 transfer Methods 0.000 abstract description 3
- 125000006850 spacer group Chemical group 0.000 abstract 3
- 238000010248 power generation Methods 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000005520 cutting process Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
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- 238000005516 engineering process Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/70—Disassembly methods
Abstract
The invention discloses a fixture and method for installing turbine buckets. The fixture is adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel, the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots. The fixture includes: a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel. The profile of a bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer of a turbine bucket thereto.
Description
Technical field
The present invention relates generally to turbine, and more specifically, relates to the fixture by using the dovetail groove of fixture (fixture) and contiguous spaced wheel to be arranged in the dovetail groove of rotor wheel by turbine rotor blade and method.
Background technology
For the rotor of turbine (such as turbine) generally from big forging process.The root receiving turbine rotor blade is generally slotted for assembling from the rotor wheel of forging cutting.Due to the demand sustainable growth to bigger turbine output and more effective turbine performance, so installing bigger and more hinged turbine rotor blade in the turbine.Relatively the turbine rotor blade of rear class is an example in turbine, and at this, movable vane is exposed to large-scale flowing, load and powerful dynamic force.Therefore, optimize these relatively rear class turbine rotor blade performance in case reduce aerodynamic losses and improve turbine thermodynamic property can be technical barrier.
Affect the dynamic characteristic of these relatively designs of rear class turbine rotor blade and include the effective length of movable vane, the pitch diameter of movable vane and the movable vane high speed of operation in both supersonic speed and subsonic flow region.Damping and movable vane fatigue are other characteristics worked in the Machine Design and their profile of movable vane.These machineries of movable vane and dynamic response characteristic and other (such as aviation timeparameter method or material select) all affect the relation between the performance of turbine rotor blade and profile.Therefore, relatively the profile of rear class turbine rotor blade generally includes the blade geometric shape of complexity, makes loss minimize for improving performance in large-scale operating condition simultaneously.
Relatively rear class turbine rotor blade is proposed some difficult problem by complex leaf geometry when being applied in and be assembled in rotor wheel by these movable vanes.Such as, the turbine rotor blade of the vicinity in rotor wheel links together typically via covering band or guard shield band, and this covering band or almuce belt ring position around the peripheral of wheel, to be limited to by working fluid in well-defined path and to increase the rigidity of movable vane.These interlocking guard shields can interfere with movable vane assembling in rotor wheel.Additionally, the inner platform of these movable vanes can include the edge being combined into one, this also can interfere with they assemblings in rotor wheel.
Summary of the invention
The first aspect of the disclosure provides fixture, this fixture is suitable to be assembled to multiple turbine rotor blades with dovetails the rotor wheel of turbine, this rotor wheel is separated with contiguous rotor wheel by spaced wheel, and this rotor wheel and this spaced wheel each have multiple dovetail groove circumferentially alignd.nullThis fixture comprises the steps that turbine rotor blade keeper，It has dovetails，This dovetails is configured to engage with in the dovetail groove of this spaced wheel，Wherein，This turbine rotor blade keeper limits movable vane keeper dovetail groove，This movable vane keeper dovetail groove has the profile of the dovetails of be configured in reception wherein and fixed turbine movable vane，Wherein，The profile of this movable vane keeper dovetail groove makes the dovetails of this turbine rotor blade and the dovetail groove substantial alignment of this rotor wheel，It it is transferred at least in part for from this spaced wheel，Wherein，The dovetails of this turbine rotor blade when being fixed in this movable vane keeper dovetail groove with the dovetail groove substantial alignment of this rotor wheel，The sidewall of this turbine rotor blade keeper engages the sidewall of circumferentially contiguous turbine rotor blade keeper collaboratively，And wherein，The dovetails of this turbine rotor blade can remove and directed for insertion into the dovetail groove of this rotor wheel slidably from this movable vane keeper dovetail groove.
The second aspect of the disclosure provides a kind of fixture, and this fixture for being assembled to the rotor wheel of turbine by multiple turbine rotor blades with dovetails, and this rotor wheel has multiple dovetail groove circumferentially alignd.This fixture comprises the steps that spaced wheel, and rotor wheel is separated by it with contiguous rotor wheel, has multiple dovetail groove circumferentially alignd；Multiple turbine rotor blade keepers, it respectively has dovetails, this dovetails is configured to engage with in the dovetail groove of this spaced wheel, wherein, each in the plurality of turbine rotor blade keeper includes dovetail groove, this dovetail groove has the profile being configured to the dovetails of in this turbine rotor blade be fixed therein, wherein, each profile of movable vane keeper dovetail groove makes the dovetails of a turbine rotor blade dovetail groove substantial alignment with this rotor wheel for being transferred to it at least in part, wherein, the dovetails of each turbine rotor blade is alignd with the dovetail groove of this rotor wheel when being fixed in movable vane keeper dovetail groove, and wherein, the essentially all of dovetails of this turbine rotor blade is suitable to remove slidably and in the directed dovetail groove to insert this rotor wheel one from movable vane keeper dovetail groove.
The third aspect of the disclosure provides the method for being assemblied in rotor wheel by multiple turbine rotor blades with dovetails, and this rotor wheel has the multiple dovetail grooves complementary with in the dovetails of this turbine rotor blade.The method comprises the steps that in multiple movable vane keeper dovetail grooves that the dovetails of the plurality of turbine rotor blade is loaded into correspondence, multiple movable vane keeper dovetail grooves of this correspondence are formed by being inserted in spaced wheel by multiple turbine rotor blade keepers, this spaced wheel includes multiple dovetail groove circumferentially alignd, and it is assemblied on armature spindle on the side of this rotor wheel, wherein, each turbine rotor blade keeper is engaged on collaboratively in the dovetail groove of this spaced wheel and includes in the plurality of movable vane keeper dovetail groove, in the plurality of movable vane keeper dovetail groove one is set as fixing wherein the dovetails of in this turbine rotor blade in yardstick；The each movable vane keeper dovetail groove being mounted with this spaced wheel of turbine rotor blade is made to align with in the dovetail groove of this rotor wheel；Dovetail groove with the alignment that each in this turbine rotor blade is transferred at least in part from this movable vane keeper dovetail groove this rotor wheel.
Technical scheme 1: a kind of fixture 100,400 being suitable to multiple turbine rotor blades 300,600 with dovetails 112 are assembled to the rotor wheel 500 of turbine, described rotor wheel 500 is separated with contiguous rotor wheel 500 by spaced wheel 200, described rotor wheel 500 and described spaced wheel 200 each have multiple dovetail groove 118,202,502 circumferentially alignd, and described fixture 100,400 includes:
nullTurbine rotor blade keeper 602，It has dovetails 112，Described dovetails 112 is configured to and the dovetail groove 118 of described spaced wheel 200、202、An engagement in 502，Wherein，Described turbine rotor blade keeper 602 limits movable vane keeper dovetail groove 118、202、502，Described movable vane keeper dovetail groove 118、202、The profile of 502 dovetails 112 be configured in reception wherein and fixing described turbine rotor blade，Wherein，Described movable vane keeper dovetail groove 118、202、The profile of 502 makes the dovetails 112 of described turbine rotor blade and the dovetail groove 118 of described rotor wheel 500、202、502 substantial alignment are transferred to it at least in part for from described spaced wheel 200，Wherein，The dovetails 112 of described turbine rotor blade is being fixed on described movable vane keeper dovetail groove 118、202、With the dovetail groove 118 of described rotor wheel 500 time in 502、202、502 substantial alignment，The sidewall of described turbine rotor blade keeper 602 engages the sidewall of circumferentially contiguous turbine rotor blade keeper 602 collaboratively，And wherein，The dovetails 112 of described turbine rotor blade can from described movable vane keeper dovetail groove 118、202、502 remove and the directed dovetail groove 118 for insertion into described rotor wheel 500 slidably、202、In 502.
Technical scheme 2: the fixture 100 according to technical scheme 1, 400, also include the turbine rotor blade keeper 602 of multiple connection, each of which has dovetails 112, described dovetails 112 is configured to and the dovetail groove 118 of described spaced wheel 200, 202, an engagement in 502, wherein, each sidewall to contiguous turbine rotor blade keeper 602 in multiple engages collaboratively, to form the multiple movable vane keeper dovetail grooves 118 being circumferentially spaced around the outer radial periphery edge of described spaced wheel 200, 202, 502, each movable vane keeper dovetail groove 118, 202, 502 profiles with the dovetails 112 being configured to receive in described turbine rotor blade.
Technical scheme 3: the fixture 100,400 according to technical scheme 1, also include holding apparatus 120, described holding apparatus 120 is attached to described turbine rotor blade keeper 602, is fixed to described spaced wheel 200 for by described movable vane keeper dovetail groove 118,202,502.
Technical scheme 4: the fixture 100,400 according to technical scheme 1, wherein, described turbine rotor blade keeper 602 includes multiple individual segments 111A, 111B, the plurality of individual segments 111A, 111B are configured to engage at least one other individual segments at its respective surfaces place, to form the profile of described turbine rotor blade keeper 602.
Technical scheme 5: the fixture 100,400 according to technical scheme 1, wherein, described turbine rotor blade keeper 602 is made up of the one in plastics and metal at least in part.
Technical scheme 6: the fixture 100,400 according to technical scheme 1, wherein, the profile of described movable vane keeper dovetail groove 118,202,502 includes fir tree, described fir tree has multiple hook portion 312, the plurality of hook portion 312 is with multiple cervical regions 310 alternately, the plurality of cervical region 310 engages with described dovetails 112, and each in the plurality of hook portion 312 has substantially flat contact surface, and described substantially flat contact surface is engaged with the dovetails 112 of turbine rotor blade.
Technical scheme 7: the fixture 100,400 according to technical scheme 1; described movable vane keeper dovetail groove 118,202,502 includes non-contact part; described non-contact part dovetails 112 with described turbine rotor blade when described turbine rotor blade keeper 602 engages with the dovetails 112 of described turbine rotor blade separates; described non-contact part limits the one in window space 318 and depression, and described depression protects a part for the dovetail groove 118,202,502 of described turbine rotor blade keeper 602.
Technical scheme 8: the fixture 100,400 according to technical scheme 1, wherein, described turbine rotor blade keeper 602 includes the one in shifting difference and interlocking fixture 100,400, for the complementary dovetails groove 118,202,502 engaging described spaced wheel 200.
Technical scheme 9: the fixture 100,400 according to technical scheme 1, wherein, described turbine rotor blade keeper 602 includes the tip edge 204 cut sth. askew.
Technical scheme 10: the fixture 100,400 of a kind of rotor wheel 500 for multiple turbine rotor blades with dovetails 112 being assembled to turbine, described rotor wheel 500 has multiple dovetail groove 118,202,502 circumferentially alignd, and described fixture 100,400 includes:
Spaced wheel 200, described rotor wheel 500 is separated by it with contiguous rotor wheel 500, has multiple dovetail groove 118,202,502 circumferentially alignd；
nullMultiple turbine rotor blade keepers 602，It each has dovetails 112，Described dovetails 112 is configured to and the dovetail groove 118 of described spaced wheel 200、202、An engagement in 502，Wherein，Each in the plurality of turbine rotor blade keeper 602 includes dovetail groove 118、202、502，Described dovetail groove 118、202、502 have and are configured to fix described turbine rotor blade 300 wherein、The profile of the dovetails 112 of in 600，Wherein，Movable vane keeper dovetail groove 118、202、Each profile of 502 makes turbine rotor blade 300、The dovetails 112 of 600 and a dovetail groove 118 of described rotor wheel 500、202、502 substantial alignment are for being transferred to it at least in part，Wherein，Each turbine rotor blade 300、The dovetails 112 of 600 is being fixed on movable vane keeper dovetail groove 118、202、With the dovetail groove 118 of described rotor wheel 500 time in 502、202、502 alignment，And wherein，Described turbine rotor blade 300、The essentially all of dovetails 112 of 600 is suitable to from movable vane keeper dovetail groove 118、202、502 remove and the directed dovetail groove 118 for insertion into described rotor wheel 500 slidably、202、In in 502 one.
Technical scheme 11: according to the fixture described in technical scheme 10, wherein, one in the plurality of turbine rotor blade keeper includes multiple individual segments, the plurality of individual segments is configured to engage at least one other individual segments at its respective surfaces place, to form the profile of described turbine rotor blade keeper.
Technical scheme 12: according to the fixture described in technical scheme 10, also include multiple holding apparatus, the plurality of holding apparatus is attached in described spaced wheel and in the plurality of turbine rotor blade keeper, wherein, turbine rotor blade keeper is fixed to described spaced wheel by each in the plurality of holding apparatus.
Technical scheme 13: according to the fixture described in technical scheme 10, wherein, each profile of movable vane keeper dovetail groove includes the window space checked providing the dovetail groove of described rotor wheel when the dovetails of described turbine rotor blade being fixed therein.
Technical scheme 14: according to the fixture described in technical scheme 10, wherein, each profile of movable vane keeper dovetail groove includes fir tree, described fir tree has multiple hook portion, the plurality of hook portion is with multiple cervical regions alternately, the plurality of cervical region engages with the dovetails of in described turbine rotor blade, and each in the plurality of hook portion has substantially flat surface, and described substantially flat surface engages with the dovetails of in described turbine rotor blade.
Technical scheme 15: according to the fixture described in technical scheme 10; wherein; described turbine rotor blade keeper includes the part separated with the dovetails of described turbine rotor blade when described turbine rotor blade keeper engages with the dovetails of described turbine rotor blade; thus limiting depression, described depression protects a part for the dovetail groove of described turbine rotor blade keeper.
Technical scheme 16: a kind of method for multiple turbine rotor blades with dovetails are arranged in rotor wheel, described rotor wheel has the multiple dovetail grooves complementary with in the dovetails of described turbine rotor blade, and described method includes:
Multiple turbine rotor blade keepers are inserted in spaced wheel, to form multiple movable vane keeper dovetail groove；
The dovetails of the plurality of turbine rotor blade is loaded in corresponding one in the plurality of movable vane keeper dovetail groove, described spaced wheel includes multiple dovetail groove circumferentially alignd and is arranged on the side of described rotor wheel on armature spindle, wherein, each turbine rotor blade keeper is engaged on collaboratively in the dovetail groove of described spaced wheel and includes in the plurality of movable vane keeper dovetail groove, and the one in the plurality of movable vane keeper dovetail groove is set as fixing wherein the dovetails of in described turbine rotor blade in yardstick；
The each movable vane keeper dovetail groove being mounted with the described spaced wheel of turbine rotor blade is made to align with in the dovetail groove of described rotor wheel；With
Each making in described turbine rotor blade is transferred to the dovetail groove of alignment of described rotor wheel at least in part from described movable vane keeper dovetail groove.
Technical scheme 17: according to the method described in technical scheme 16, before being additionally included in the multiple dovetails loading described turbine rotor blade, each in described turbine rotor blade keeper is fixed to described spaced wheel.
Technical scheme 18: according to the method described in technical scheme 16, removes described turbine rotor blade keeper from the corresponding dovetail groove of described spaced wheel after being additionally included in the dovetail groove that described turbine rotor blade is transferred to described rotor wheel at least in part.
Technical scheme 19: according to the method described in technical scheme 16, also include repeating described dovetails load and each in described turbine rotor blade is from described movable vane keeper dovetail groove at least part of transfer of the dovetail groove of the alignment of described rotor wheel, until the last circumferential dovetail groove on described spaced wheel stays open at loading space place.
Technical scheme 20: according to the method described in technical scheme 19, also include:
At described loading space place, last remaining turbine rotor blade is axially inwardly inserted in above the last circumferential dovetail groove of described spaced wheel,
Final turbine rotor blade keeper is axially inwardly inserted between the last circumferential dovetail groove of described last remaining turbine rotor blade and described spaced wheel.
Accompanying drawing explanation
Fig. 1 is in the schematic diagram of the generation system powered by conventional energy of gas turbine form.
The cross section that Fig. 2 is the turbine rotor blade keeper of an embodiment according to the disclosure illustrates.
Fig. 3 is that another cross section according to the turbine rotor blade keeper that embodiment of the disclosure illustrates.
The perspective partial that Fig. 4 is the spaced wheel of an embodiment according to the disclosure cuts illustration open, and this spaced wheel has multiple dovetail groove circumferentially alignd and is inserted in turbine rotor blade keeper therein.
Fig. 5 is the partial section according to the turbine rotor blade dovetails that embodiment of the disclosure and turbine rotor blade keeper dovetail groove.
The perspective partial that Fig. 6 is the spaced wheel of an embodiment according to the disclosure cuts illustration open, and this spaced wheel has in some dovetail grooves in turbine rotor blade keeper and some in this turbine rotor blade keeper and has turbine rotor blade.
The side that Fig. 7 is the spaced wheel with turbine rotor blade keeper of the adjacent rotor wheel of an embodiment according to the disclosure illustrates, and turbine rotor blade is just loaded the dovetail groove to rotor wheel from the turbine rotor blade keeper of spaced wheel.
The perspective partial that Fig. 8 is the spaced wheel of an embodiment according to the disclosure cuts illustration open, and one of them dovetail groove does not have turbine rotor blade keeper and turbine rotor blade therein.
The perspective partial that Fig. 9 is the rotor wheel of an embodiment according to the disclosure cuts illustration open, the final turbine rotor blade that one of them dovetail groove inserts with having positive radial.
Detailed description of the invention
Spatial relationship term, such as " interior ", " outward ", " ... under ", " ... below ", " relatively low ", " ... above ", " higher ", " import ", " outlet " etc. can be used herein for the simplification described, and describes an element illustrated in the accompanying drawings or the feature relation relative to another (multiple) element or (multiple) feature.Spatial relationship term can be intended to contain the device except the orientation drawn in the accompanying drawings in use or operation be differently directed or.Such as, if the device in accompanying drawing is overturn, then be described as the element of other elements or feature " below " or " under " will be orientated in other elements or feature " on ".Therefore, example term " ... can be encompassed in below " ... above with in ... both orientations below.This device can be otherwise directed (90-degree rotation or be in other directed), and correspondingly explains spatial relation description symbol used herein.
With reference to Fig. 1, it is shown that be in the generation system 10 powered by conventional energy of turbine form.Embodiment of the disclosure to be applicable to and use together with power generation system 10 (such as, air cooled gas turbine), and/or can be integrated in its component.Power generation system 10 is exemplarily shown as the turbine assembly based on burning, although embodiment of the disclosure and could be applicable to use together with applicable other kinds of turbine.In the turbine based on burning, typically lie in including the burner 12 of multiple fuel nozzles 14 between the turbine component 18 of compressor 16 and power generation system 10.Compressor 16 and turbine component 18 can be mechanically coupled to each other by rotatable shaft 20.
Air 22 flows through compressor 16, burner 12 and turbine component 18 successively.The compression provided by compressor 16 also can increase the temperature of air 22.(multiple) fuel nozzle 14 can provide fuel into burner 12, and at this, fuel burns when there are air 22 to form hot gas thread.Hot gas thread from burner 12 can enter turbine component 18, such as mechanical energy is applied to rotatable shaft 20 by making one group of turbine rotor blade rotate, thus power transmission is back to compressor 16 and/or is mechanically coupled to any load (not shown) of rotatable shaft 20.Power generation system 10 may be included in the compressor inlet 24 before compressor 16, although can provide this air to compressor 16 before being compressed and be delivered to burner 12 by air.Although not being specifically illustrated in FIG, but power generation system 10 can include the multiple levels with related burner 12, compressor 16 and/or turbine 18.Power generation system 10 can be also one in the some independent turbine controlled by same operator, and/or can be a part for bigger power generation system.
With reference to accompanying drawing, Fig. 2 illustrates fixture 100, and this fixture 100 for being assembled to the rotor wheel (not shown) of turbine by the dovetail projection (in Fig. 2 not shown) from turbine rotor blade.Some spaced wheels can by rotor wheel axially proximate with it for each rotor wheel in turbine separately.In operation, the dovetail groove of the engageable rotor wheel of fixture 100, to provide component and the place that can assemble and/or engage turbine rotor blade.There is complementary dovetail groove in the engageable fixture 100 of turbine rotor blade of dovetail projection thereon.Each turbine rotor blade can be mechanically coupled to spaced wheel by fixture 100.Dovetail groove in fixture 100 can substantially axially align (that is, substantially aliging) along the direction of rotor with the dovetail groove of the similarly sized and profile of the rotor wheel of adjacent partition wheel.Turbine rotor blade can axially be transferred to the dovetail groove of contiguous rotor wheel at least in part from fixture 100.As used herein, term " transfer " or " axially displaced " refer to turbine rotor blade from a position (such as passing through sliding motion) the mobile process to another location, the dovetail groove of the rotor wheel such as moved adjacent between the dovetail groove in fixture 100.Therefore, the embodiment of fixture 100 and other fixtures discussed herein can allow to be arranged in turbine turbine rotor blade when being not directly contacted with spaced wheel.Embodiment of the disclosure the method also provided for by using the embodiment of fixture 100 to install turbine rotor blade.
Fixture 100 can include turbine rotor blade keeper 110 or be in the form of turbine rotor blade keeper 110, and exemplarily, figure 2 illustrates and discuss in this article single turbine rotor blade keeper 110.Discuss the exemplary characteristics of turbine rotor blade keeper 110, to illustrate the use of itself and other components further, including other turbine rotor blade keepers 110.Turbine rotor blade keeper 110 can be single component or can be made up of multiple individual segments 111A, the 111B contacted each other along particular surface (illustrating with imaginary line in fig. 2).When engaging another individual segments 111A, 111B, individual segments 111A, 111B can form the profile of turbine rotor blade keeper.Turbine rotor blade keeper 110 is shown as in fig. 2 and includes two individual segments 111A, 111B, it is to be understood that the individual segments of any desired quantity can be used in embodiment of the disclosure.Individual segments 111A, 111B can by the physical contact between corresponding surface, welding, complementary manufacture or processing and/or for provide between two components be placed adjacent to or other processes of mechanical attachment engage each other.Turbine rotor blade keeper 110 can be made up of various structural materials, to adapt to application-specific, and such as can be embodied as plastic member, steel forms or include the hardware of steel and/or have the component of combination of pottery and/or metallics.
Dovetails 112 can extend from turbine rotor blade keeper 110 and can shape, dimensioning or be otherwise configured to engages the dovetail groove of the spaced wheel being positioned between two or more respective rotor wheel.Contiguous spaced wheel can include again some dovetail grooves circumferentially alignd.The part of turbine rotor blade keeper 110 can laterally extend specific range w in one direction from dovetails 1121And another distance w is laterally extended along different directions2.Distance w1、w2It is substantially equal to maybe can differ each other predetermined value so that turbine rotor blade keeper 110 laterally extends farther with compared with opposite sides from dovetails 112 on a side.In the figure 2 example, distance w1Exemplarily it is shown as and is noticeably greater than w2.Under any circumstance, there is various sizes of distance w1、w2Can provide such as turbine rotor blade keeper 110 directed physical guide during installation or reference so that each turbine rotor blade keeper 110 (and/or its individual segments 111A, 111B) will be installed along specific direction and/or orientation.
Such as discussing elsewhere in this article, the dovetail groove of spaced wheel can align at least in part with the dovetail groove of one or more contiguous rotor wheel.Turbine rotor blade keeper 110 may also include the profile 114 on dovetails 112 surface, to engage the corresponding dovetail groove using turbine rotor blade keeper 110 in spaced wheel matchingly.Two sidewalls 116 of turbine rotor blade keeper 110 can be shaped to engage other turbine rotor blade keepers 110 during operation, such as describing elsewhere in this article.
Turbine rotor blade keeper 110 can include dovetail groove 118 and for receiving, keep and/or engage matchingly other features of the contour surface of particular elements, for instance, turbine rotor blade dovetail projection.Dovetail groove 118 can be positioned between two sidewalls 116.As in figure 2 it is shown, the dovetails 112 of the most inner region of the dovetail groove 119 projected above in turbine rotor blade keeper 110 can form the component of generally C-shape and/or Y shape.Holding apparatus 120 can optionally provide on turbine rotor blade keeper 110, is attached to turbine rotor blade keeper 110 and/or is integrally formed with turbine rotor blade keeper 110.Holding apparatus 120 can be at the form of one or more mechanical component for a structure is attached to another structure, includes but not limited to: holds bolt, binding agent, track, solid flexible member, coupling member and/or is used for being retained in another by a component and/or holding as machinery adjacent thereto.In operation, holding apparatus 120 is movable to and actuates or locked position, for instance, contact interval is taken turns, to hinder or to stop the axially-movable of turbine rotor blade keeper 110.The turbine rotor blade keeper 110 of fixture 100 can be fixed in installation site by these features of holding apparatus 120.Holding apparatus 120 can extend across and/or be attached to one or more axial sides of turbine rotor blade keeper 110.In an embodiment, holding apparatus 120 can be at extending axially through the form of the bar of turbine rotor blade keeper 110, and manipulation point (such as handle) that can include in particular side with engagement and/or departs from holding apparatus 120.It will further be understood that holding apparatus 120 can be at the form of multiple component, it is no matter with complimentary to one another or with independent of each other.
Other features of turbine rotor blade keeper 110 and component can provide or strengthen the mechanical attachment between turbine rotor blade keeper 110 and spaced wheel.As shown in by the example in Fig. 2 and 3, turbine rotor blade keeper 110 can include having respective distances w1、w2Two individual segments 111A, 111B and/or there is the first width (w1) first surface 122 (such as, face forward surface) and there is the second width (w2) second surface 124 (such as, towards after surface).Difference between the width on individual segments 111A, 111B and/or the first and second surfaces 122,124 can form " shifting difference ", and (that is, the size difference between two correspondences and/or opposed surface, in figure 3 by DSkewMark), it for maintaining the certain orientation of turbine rotor blade keeper 110 when being arranged in spaced wheel.In addition or alternatively, turbine rotor blade keeper 110 can include interlocking fixture 126 (being shown in phantom line), be similar to those in key or of bonding device, for engagement be positioned on turbine spaced wheel or complementary fixture.In the example of fig. 3, interlocking fixture 126 is shown as the projection from turbine rotor blade keeper 110, but alternatively can be at removing from the structure of turbine rotor blade keeper 110 and/or with the form of the groove of its one or ridge.Interlocking fixture 126 can keep the expectation set of turbine rotor blade keeper 110 during installation, to stop the contrary installation of such as turbine rotor blade keeper 110.
Forward Fig. 4 to, it is shown that some turbine rotor blade keepers 110 of the fixture 100 of engagement spaced wheel 200.Each dovetails 112 of specific turbine rotor blade keeper 110 can be formed for the given shape of the corresponding dovetail groove 202 of engagement spaced wheel 200, thus allowing turbine rotor blade keeper 110 to be circumferentially arranged around spaced wheel 200.In the exemplary embodiment, the dovetails 112 of turbine rotor blade keeper 110 can include (chamfered) tip edge 204 of cutting sth. askew relative to the remainder of its structure.In order to complementary with dovetails 112, dovetail groove 202 can be at cutting sth. askew the form of groove, and this groove of cutting sth. askew removes from the structure of spaced wheel 200, etch into this structure or is otherwise formed in this structure.When dovetails 112 includes beveled tip edge 204, dovetail groove 202 can be at the shape of complementary groove, fixture etc., for the component receiving dovetails 112 and/or similar profile.Turbine rotor blade keeper 110 can receive turbine rotor blade and is fixed on by turbine rotor blade in they corresponding dovetail grooves 118, thus allowing the part of each turbine rotor blade to be fixed to spaced wheel 200 by one or more turbine rotor blade keeper 110 of fixture 100.
Each dovetail groove 202 of spaced wheel 200 can spaced apart or otherwise position, for dovetail groove substantial alignment corresponding to rotor wheel, thus allowing the corresponding dovetail groove substantial alignment or otherwise continuous of dovetail groove 118 and contiguous rotor wheel.As used herein, term " substantially aligned " or " substantial alignment " refer to two components (such as, groove) between any alignment, this permits single component (such as, turbine rotor blade dovetails) and extends through the dovetail groove 118 of turbine rotor blade keeper 110 and other dovetail grooves and/or shift between which without being initially treated or revising.In embodiment of the disclosure, when turbine rotor blade is positioned between two rotor wheel, the dovetail groove 118 of turbine rotor blade keeper 110 and and the dovetail groove of contiguous rotor wheel between the substantially aligned dovetail groove 118 allowing turbine rotor blade to be positioned at turbine rotor blade keeper 110 in and be transferred to the dovetail groove 118 of turbine rotor blade 110 at least in part.
After turbine rotor blade keeper 110 being placed in the dovetail groove 202 of spaced wheel 200, the sidewall 116 of turbine rotor blade keeper 110 can engage each other (such as collaboratively, by direct or indirect contact), so that each turbine rotor blade keeper 110 is fixed and is maintained on spaced wheel 200.Fixture 100 can be embodied as multiple turbine rotor blade keeper 110, and wherein corresponding dovetail groove is circumferentially spaced around the outer radial periphery edge of spaced wheel 200.Each turbine rotor blade keeper 110 and/or its individual segments 111A, 111B (Fig. 2) can with independently of one another, and any amount of turbine rotor blade keeper can be provided.Turbine rotor blade keeper 110 may together form the arc segment of particular element (such as, spaced wheel) and/or the complete circumference group of turbine rotor blade keeper 110.Turbine rotor blade keeper 110 can with independent of one another and/or be connected by the making etc. of screwed joint, welding, complementary processing and/or each turbine rotor blade keeper 110 (or its sections).Turbine rotor blade group may be installed in each turbine rotor blade keeper 110 circumferentially positioned of fixture 100.
Turbine rotor blade keeper 110 can include for strengthen its purposes and/or with the feature engaged of spaced wheel 200.Such as, the dovetail groove 202 of spaced wheel 200 can be set as allowing the slip in some yardsticks or in only one yardstick to move and/or engage in yardstick so that can insert or remove the turbine rotor blade keeper 110 of fixture 100 as required.Shifting difference DSkew(Fig. 3) and interlocking fixture 126 (Fig. 3) also can limit the point that turbine rotor blade keeper 110 is completely inserted in specific dovetail groove 202, and can hinder along incorrect direction or exceed the slip of predetermined restriction and move and/or engage.The feature of some turbine rotor blade keepers 110 may be in the dovetail groove 118 with difformity, size, width etc..In this case, turbine rotor blade keeper 110 is changed as required or replaces the turbine rotor blade keeper 110 with different dovetail groove 118, for application-specific.As further illustrated in Figure 5, when turbine rotor blade keeper 110 is received in wherein, what the profile of one or more dovetail groove 118 in turbine rotor blade keeper 110 may be provided in the corresponding dovetail groove in the rotor wheel contiguous with spaced wheel 200 axially checks (axialview).
In fig. 5, it is shown that the geometric properties engaged between turbine rotor blade 300 with turbine rotor blade keeper 110.Fig. 5 includes the sectional view of turbine rotor blade keeper 110, and this turbine rotor blade keeper 110 engages turbine rotor blade 300 by receiving dovetail projection 302 in dovetail groove 118.During having the operation of turbine of turbine rotor blade keeper 110 and turbine rotor blade 300, turbine rotor blade 300 can move (such as, by rotating) as a kind of blade when being actuated against its surface by fluid stream.The dovetail groove 118 of turbine rotor blade keeper 110 can include having substantially wavy or " Cunninghamia lanceolata (Lamb.) Hook. " shape, plurality of cervical region 310 is with hook portion 312 (such as, it is in the form of projection or similar surfaces) alternately, for the surface of the similar profile of engagement turbine rotor blade 300 when being with or without the directly contact spreading all over dovetail groove 118 between two components.Each cervical region 310 can include substantially flat contact surface, for the dovetails of engagement turbine rotor blade 300.Although the cross section that dovetail groove 118 is exemplarily shown as with turbine rotor blade 300 is substantially complementary, it is to be understood that, dovetail groove 118 can be any desired shape or geometry, such as, substantially the groove of v shape, one or more triangle wedge, rectangle or semi-circular groove, the groove etc. that formed with compound geometry.
Some hook portions 312 can include non-contact part (such as, surface), and this non-contact part separates with the dovetails of turbine rotor blade 300 when turbine rotor blade keeper 110 engages turbine rotor blade 300.These non-contact part can limit one group of depression 314 between turbine rotor blade keeper 110 and turbine rotor blade 300.Depression 314 can relative to the part of the dovetail groove 118 by protection turbine rotor blade keepers 110 such as the CONTACT WITH FRICTION that such as manufacturing between turbine rotor blade 300 changes between damage, oscillating movement or damage, exterior vibration and event, two components caused.Can such as by remove from turbine rotor blade keeper 110 material part and/or otherwise manufacture or amendment turbine rotor blade keeper 110 form depression 314 to limit depression 314.Especially, depression 314 can stop turbine rotor blade keeper 110 to contact turbine rotor blade 300 at sensitive part place.In operation, turbine rotor blade keeper 110 and turbine rotor blade 300 can contact surface 316 place at one group that spreads all over that dovetail groove 118 is distributed with turbine rotor blade 300 and engage each other.Depression 314 also by manufacturing, amendment and/or otherwise processing turbine rotor blade 300 to form separating and formed between turbine rotor blade 300 with dovetail groove 118.
Dovetail projection 302 can include elevational dimension H, and this elevational dimension H has the size less than the respective heights yardstick of dovetail groove 118.These different height may be formed at the interval difference between two components, and limits window space 318.Although exemplarily illustrating a window space 318 in Figure 5, it is to be understood that, in embodiment of the disclosure, multiple window space 318 can be limited between turbine rotor blade keeper 110 and turbine rotor blade 300.It will further be understood that depression 314 can also function at least part of window, for providing checking between turbine rotor blade keeper 110 and turbine rotor blade 300 (can apply at this place).When dovetail projection 302 is arranged in turbine rotor blade keeper 110, window space 318 may be present between dovetail groove 118 and dovetail projection 302.When dovetail projection 302 positions and/or is fixed in dovetail groove 118, window space 318 can provide axially checking of the dovetail groove of the alignment of rotor wheel (not shown).In Figure 5 exemplarily, turbine rotor blade 300 is shown as and includes dovetail projection 302 and turbine rotor blade keeper 110 is shown as and includes dovetail groove 118.In an alternative embodiment, turbine rotor blade keeper 110 can include dovetail groove but not dovetail projection 302.In this case, in an alternative embodiment, turbine rotor blade keeper 110 can be revised or reverse, to permit from engaging between turbine rotor blade keeper 110 complementary dovetails projection (such as, dovetails 112 (Fig. 2)) and the dovetail groove of turbine rotor blade keeper 300.When these amendments and/or alternative are in current, other features discussed in this article can suitably be changed and/or keep identical.
Forwarding Fig. 6 to, embodiment of the disclosure and can include fixture 400, this fixture 400 is for being assembled to rotor wheel by some turbine rotor blades with dovetails.Fixture 400 can include or be connected to one or more spaced wheel 200, and this spaced wheel 200 is positioned between two circumferentially contiguous rotor wheel (not shown).Circumferentially contiguous turbine rotor blade keeper 110 can such as by the contact between their sidewall 116 (Fig. 1,3) come with coordination with one another engage.Each spaced wheel 200 can include spreading all over multiple dovetail grooves 202 circumferentially alignd that its outer radial face is circumferentially distributed.Fixture 400 can include some turbine rotor blade keepers 110, and these some turbine rotor blade keepers 110 engage the dovetail groove 202 of spaced wheel 200 by means of dovetails 112 thereon.The dovetail groove 118 of turbine rotor blade keeper 110 radially can shift from dovetails 112 relative to spaced wheel 200.The dovetail groove 118 of each turbine rotor blade keeper 110 can be set as being fixed therein the dovetail projection 302 of turbine rotor blade 300 in shape and/or yardstick.As shown in Figure 6, the engageable spaced wheel 200 of turbine rotor blade keeper 110, and the feature limited by the separating distance between spaced wheel 200 and one or more turbine rotor blade keeper 110 can be included alternatively, such as, with those the similar depressions illustrated in this article and discuss and window space (such as, depression 314 (Fig. 3) and window space (318)).
Some turbine rotor blades 300 thereon with dovetail projection 302 may be installed in fixture 400 and/or are attached to fixture 400.Dovetail projection 302 can be set as engaging with in some dovetail grooves 202 of spaced wheel 200 in shape, yardstick etc..When the dovetail projection 302 of turbine rotor blade 300 engages dovetail groove 118, form the mechanical attachment between turbine rotor blade 300 and spaced wheel 200.Turbine rotor blade 300, by turbine rotor blade keeper 110, the mechanical attachment of spaced wheel 200 can be stoped such as direct physical contact between spaced wheel 200 and each turbine rotor blade 300.Axially aligning between turbine rotor blade 300 and the complementary member of rotor wheel also can be formed by the mechanical attachment of turbine rotor blade keeper 110.
Forward Fig. 7 to, it is shown that the embodiment of fixture 400 and rotor wheel 500.The dovetail groove 118 of turbine rotor blade keeper 110 may be positioned to the corresponding dovetail groove 502 with rotor wheel 500 when engaging spaced wheel 200 and at least substantially aligns.Shape and/or the yardstick of the dovetail groove 118 of turbine rotor blade keeper 110 can provide passage, guide in the dovetail groove 502 being inserted into fixture 400 and rotor wheel 500 for by turbine rotor blade 300.In operation, fixture 400 can structurally support turbine rotor blade 300, and permits being transferred to rotor wheel 500 at least in part.After installing fixture 400, the dovetail groove 118 of each turbine rotor blade keeper 110 can with dovetail groove 502 substantial alignment of rotor wheel 500.Turbine rotor blade 300 can move (such as, passing through sliding motion) between the dovetail groove 118,502 of turbine rotor blade keeper 110 and rotor wheel 500.
Some turbine rotor blade keepers 110 of fixture 400 with connecting each other or can contact.That is, turbine rotor blade keeper 110 providing sidewall 116 (Fig. 1,3) or interlocking fixture 126 (Fig. 3), coupling member etc. of vicinity thereon and can contact with each other.Fixture 400 may also include one or more holding apparatus 120 (Fig. 2), this one or more holding apparatus 120 is attached to such as turbine rotor blade keeper 110 or spaced wheel 200, turbine rotor blade 300 to be fixed to fixture 400 (such as, at spaced wheel 200 place) and rotor wheel 500.Except the dovetail groove 118 of turbine rotor blade keeper 110, the dovetail groove 502 of rotor wheel 500 can include at least some shown in Fig. 5 and in the geometric properties discussed elsewhere herein.Specifically, dovetail groove 118,502 can be at wavy or " Cunninghamia lanceolata (Lamb.) Hook. " shape form, wherein there is multiple cervical region 310 (Fig. 5) and hook portion 310 (Fig. 5) thereon, for the dovetail projection 302 at corresponding flat surfaces place engagement turbine rotor blade 300.Dovetail groove 118,502 also can be set as one or more depression 314 (Fig. 5) being limited between dovetail groove 118,502 and the dovetail projection 302 of turbine rotor blade 300 in profile and/or yardstick, to protect the corresponding part of dovetail groove 118,502.It being understood that and embodiment of the disclosure and be applicable to following rotor wheel 500, this rotor wheel 500 is configured to different types of turbine rotor blade 300, (that is, non-flat forms) the axial entrance turbine rotor blade (not shown) such as bent.The shape of turbine rotor blade keeper 110, axial profile and/or orientation can be revised, for this application applicatory.
Forward Fig. 8 to, embodiment of the disclosure provide for turbine rotor blade is arranged in rotor wheel and/or on method.More specifically, can include being assembled in rotor wheel 200 some turbine rotor blades 300 with dovetail projection 302 according to disclosed method.The dovetail groove 202 of rotor wheel 200 can be set as in size, yardstick etc. that the dovetail projection 302 with in turbine rotor blade 300 is complementary.The dovetail projection 302 of some turbine rotor blades 300 can each be loaded in the corresponding dovetail groove 118 of a turbine rotor blade keeper 110 (such as, in axial direction).The dovetails 112 of each turbine rotor blade keeper 110 can be plugged in one in the some dovetail grooves 202 circumferentially positioned around spaced wheel 200.Disclosed method can include one or more turbine rotor blade keeper 110 is fixed to spaced wheel 200, for instance, by actuating and/or lock holding apparatus 120, this holding apparatus 120 is attached to spaced wheel 200 or turbine rotor blade keeper 120.Each dovetail groove 202 of spaced wheel 200 can radially shift from corresponding dovetail groove 502 (Fig. 7) and circumferentially position around rotor wheel 500 (Fig. 7).Each turbine rotor blade keeper 110 can engage the dovetail groove 202 of correspondence collaboratively by dovetails 112, thus the dovetail projection 302 of turbine rotor blade 300 is fixed to the radial position of the dovetail groove 202 of spaced wheel 200.
Forward Fig. 9 to, it is shown that according to the additive method step that embodiment of the disclosure.Figure 8 illustrates and after the loading step discussed elsewhere in this article, the dovetail groove 118 of each turbine rotor blade keeper 110 wherein with turbine rotor blade 300 at least can align basically with the specific dovetail groove 502 of rotor wheel 500.At least basic alignment formed between dovetail groove 118,502 can allow turbine rotor blade 300 to be transferred to rotor wheel 500 at least in part from turbine rotor blade keeper 110 in ensuing process steps.Specifically, can include transferring to the dovetail groove 504 of alignment or rotor wheel 500 (such as, by moving axially) turbine rotor blade 300 at least in part from turbine rotor blade keeper 110 according to disclosed method.
Can include being loaded on turbine rotor blade keeper 110 by turbine rotor blade 300 with predefined procedure or mode according to disclosed method, and turbine rotor blade 300 is transferred in rotor wheel 500 at least in part.Step for loading and shift at least in part turbine rotor blade 300 discussed herein is repeatable, until a dovetail groove 202 (Fig. 3,5-8) of rotor wheel 200 (Fig. 3,5-8) stays open at specific loading space place.Final turbine rotor blade 600 can load when not using turbine rotor blade keeper 110 and load at least in part to rotor wheel 500 at first.Final turbine rotor blade 600 can by being inserted in the dovetail groove 502 being transferred to rotor wheel 500 between two turbine rotor blades 300 at least in part radially so that this final turbine rotor blade shifts spatially from the last idle dovetail groove 202 of rotor wheel 200.Then final turbine rotor blade keeper 602 can be axially inserted in the gap between the dovetail groove 202 of spaced wheel 200 and final turbine rotor blade 600 so that final turbine rotor blade 600 is structurally supported by both final turbine rotor blade keeper 602 and rotor wheel 500.
Embodiment of the disclosure and some technology and business can be provided to arrange, exemplarily discuss some of which in this article.Fixture discussed herein and the embodiment of method can provide substantially consistent manufacture and/or the assembling of rotating member (those such as use in the turbine).Embodiment of the disclosure and can be additionally used in the process and/or event needing dismounting rotating member and/or stage of turbine at least in part, such as during checking the hot gas path section of particular elements (such as, three grades of movable vanes of steam or gas turbine).The application with the fixture of turbine rotor blade keeper may also allow for installing and removing turbine rotor blade, without first taking out rotor from the housing of rotor.It being understood that embodiment of the disclosure can provide under other operations and/or maintenance situation in this article concrete propose advantage and feature.
Term used herein is only used for describing specific embodiment and being not intended to limit the disclosure.As it is used in the present context, singulative " ", " one " and " being somebody's turn to do " intention also include plural form, unless context clearly dictates otherwise.It is also to be understood that, where used in this disclosure, term " includes " and/or the existence of the feature, entirety, step, operation, element and/or the component that describe is described " including ... ", but is not excluded for the existence of other features one or more, entirety, step, operation, element, component and/or their combination.
This written explanation uses example with the open present invention, including preferred forms, and enables any those skilled in the art to put into practice the present invention, including manufacturing and using any equipment or system and the method carrying out any merging.The patentable scope of the present invention is defined by the claims, and can comprise other examples that those skilled in the art expect.If these other examples include not different from the literal language of claim structural details, if or these other examples include the equivalent structural elements without marked difference of the literal language with claim, then these other examples are intended within the scope of the claims.
Claims (10)
1. the fixture (100,400) being suitable to multiple turbine rotor blades (300,600) with dovetails (112) are assembled to the rotor wheel (500) of turbine, described rotor wheel (500) is separated with contiguous rotor wheel (500) by spaced wheel (200), described rotor wheel (500) and described spaced wheel (200) each have multiple dovetail groove (118,202,502) circumferentially alignd, and described fixture (100,400) including:
nullTurbine rotor blade keeper (602)，It has dovetails (112)，Described dovetails (112) is configured to and the dovetail groove (118 of described spaced wheel (200)、202、502) engagement in，Wherein，Described turbine rotor blade keeper (602) limits movable vane keeper dovetail groove (118、202、502)，Described movable vane keeper dovetail groove (118、202、502) there is the profile of the dovetails (112) of be configured in reception wherein and fixing described turbine rotor blade，Wherein，Described movable vane keeper dovetail groove (118、202、502) profile makes the dovetails (112) of described turbine rotor blade and the dovetail groove (118 of described rotor wheel (500)、202、502) substantial alignment is transferred to it at least in part for from described spaced wheel (200)，Wherein，The dovetails (112) of described turbine rotor blade is being fixed on described movable vane keeper dovetail groove (118、202、502) with the dovetail groove (118 of described rotor wheel (500) time in、202、502) substantial alignment，The sidewall of described turbine rotor blade keeper (602) engages the sidewall of circumferentially contiguous turbine rotor blade keeper (602) collaboratively，And wherein，The dovetails (112) of described turbine rotor blade can from described movable vane keeper dovetail groove (118、202、502) remove slidably and the directed dovetail groove (118 for insertion into described rotor wheel (500)、202、502) in.
2. fixture (100 according to claim 1, 400), also include the turbine rotor blade keeper (602) of multiple connection, each of which has dovetails (112), described dovetails (112) is configured to and the dovetail groove (118 of described spaced wheel (200), 202, 502) engagement in, wherein, each sidewall to contiguous turbine rotor blade keeper (602) in multiple engages collaboratively, to form the multiple movable vane keeper dovetail grooves (118 being circumferentially spaced around the outer radial periphery edge of described spaced wheel (200), 202, 502), each movable vane keeper dovetail groove (118, 202, 502) there is the profile of the dovetails (112) being configured to receive in described turbine rotor blade.
3. fixture according to claim 1 (100,400), also include holding apparatus (120), described holding apparatus (120) is attached to described turbine rotor blade keeper (602), is fixed to described spaced wheel (200) for by described movable vane keeper dovetail groove (118,202,502).
4. fixture according to claim 1 (100,400), wherein, described turbine rotor blade keeper (602) includes multiple individual segments (111A, 111B), the plurality of individual segments (111A, 111B) is configured to engage at least one other individual segments at its respective surfaces place, to form the profile of described turbine rotor blade keeper (602).
5. fixture according to claim 1 (100,400), wherein, described turbine rotor blade keeper (602) is made up of the one in plastics and metal at least in part.
6. fixture according to claim 1 (100,400), wherein, the profile of described movable vane keeper dovetail groove (118,202,502) includes fir tree, described fir tree has multiple hook portion (312), the plurality of hook portion (312) is with multiple cervical regions (310) alternately, the plurality of cervical region (310) engages with described dovetails (112), each in the plurality of hook portion (312) has substantially flat contact surface, and described substantially flat contact surface is engaged with the dovetails (112) of turbine rotor blade.
7. fixture according to claim 1 (100,400); described movable vane keeper dovetail groove (118,202,502) includes non-contact part; described non-contact part dovetails (112) with described turbine rotor blade when described turbine rotor blade keeper (602) is engaged with the dovetails of described turbine rotor blade (112) separates; described non-contact part limits the one in window space (318) and depression, and described depression protects a part for the dovetail groove (118,202,502) of described turbine rotor blade keeper (602).
8. fixture according to claim 1 (100,400), wherein, described turbine rotor blade keeper (602) includes the one in shifting difference and interlocking fixture (100,400), for the complementary dovetails groove (118,202,502) engaging described spaced wheel (200).
9. fixture according to claim 1 (100,400), wherein, described turbine rotor blade keeper (602) includes the tip edge (204) cut sth. askew.
10. the fixture (100,400) being used for multiple turbine rotor blades with dovetails (112) are assembled to the rotor wheel (500) of turbine, described rotor wheel (500) has multiple dovetail groove (118,202,502) circumferentially alignd, and described fixture (100,400) including:
Spaced wheel (200), described rotor wheel (500) is separated by it with contiguous rotor wheel (500), has multiple dovetail groove (118,202,502) circumferentially alignd；
nullMultiple turbine rotor blade keepers (602)，It each has dovetails (112)，Described dovetails (112) is configured to and the dovetail groove (118 of described spaced wheel (200)、202、502) engagement in，Wherein，Each in the plurality of turbine rotor blade keeper (602) includes dovetail groove (118、202、502)，Described dovetail groove (118、202、502) have and be configured to fix described turbine rotor blade (300 wherein、600) profile of the dovetails (112) of in，Wherein，Movable vane keeper dovetail groove (118、202、502) each profile makes turbine rotor blade (300、600) dovetail groove (118 of dovetails (112) and described rotor wheel (500)、202、502) substantial alignment is for being transferred to it at least in part，Wherein，Each turbine rotor blade (300、600) dovetails (112) is being fixed on movable vane keeper dovetail groove (118、202、502) with the dovetail groove (118 of described rotor wheel (500) time in、202、502) alignment，And wherein，Described turbine rotor blade (300、600) essentially all of dovetails (112) is suitable to from movable vane keeper dovetail groove (118、202、502) remove slidably and the directed dovetail groove (118 for insertion into described rotor wheel (500)、202、502) in.
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|---|---|---|---|
| US14/594,379 US10125635B2 (en) | 2015-01-12 | 2015-01-12 | Fixture and method for installing turbine buckets |
| US14/594379 | 2015-01-12 |
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| CN105781625A true CN105781625A (en) | 2016-07-20 |
| CN105781625B CN105781625B (en) | 2020-03-31 |
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| CN201610017156.XA Active CN105781625B (en) | 2015-01-12 | 2016-01-12 | Fixture and method for mounting turbine buckets |
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| EP (1) | EP3043029B1 (en) |
| JP (1) | JP6730031B2 (en) |
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| EP2944775A1 (en) * | 2014-05-12 | 2015-11-18 | Siemens Aktiengesellschaft | Method for assembling a turbine assembly |
| US10016864B2 (en) * | 2015-01-02 | 2018-07-10 | The Boeing Company | System and method of securing a component in position for machining using a fixture assembly |
| US10100677B2 (en) * | 2016-09-27 | 2018-10-16 | General Electric Company | Fixture for restraining a turbine wheel |
| US10024164B2 (en) * | 2016-09-27 | 2018-07-17 | General Electric Company | Fixture for restraining a turbine wheel |
| EP3336315B1 (en) * | 2016-12-13 | 2021-09-15 | General Electric Company | Fixture for transfering turbine blades to a rotor wheel |
| US10883386B2 (en) * | 2017-06-21 | 2021-01-05 | Mitsubishi Hitachi Power Systems Americas, Inc. | Methods and devices for turbine blade installation alignment |
| DE112018007789T5 (en) * | 2018-07-31 | 2021-04-01 | General Electric Company | COMPONENT WITH MECHANICAL INTERACTIVE FEATURES WITH ADAPTIVE COOLING AND MANUFACTURING PROCESS |
| RU192036U1 (en) * | 2019-05-22 | 2019-09-02 | Акционерное общество (АО) "Научно-исследовательский институт "Лопастных машин" ("НИИ ЛМ") | Vane Impeller with Radial Trowel |
| US11794830B2 (en) * | 2021-01-22 | 2023-10-24 | Caterpillar Inc. | Sprocket locking segments |
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- 2015-01-12 US US14/594,379 patent/US10125635B2/en active Active
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- 2016-01-07 JP JP2016001422A patent/JP6730031B2/en active Active
- 2016-01-11 EP EP16150815.5A patent/EP3043029B1/en active Active
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110154631A1 (en) * | 2009-12-30 | 2011-06-30 | General Electric Company | Fixture and method for mounting articulated turbine buckets |
| US20140112794A1 (en) * | 2012-06-12 | 2014-04-24 | General Electric Company | Blade attachment assembly |
| CN203685307U (en) * | 2012-08-14 | 2014-07-02 | 通用电气公司 | Turbine, cover piece and cover piece system |
Also Published As
| Publication number | Publication date |
|---|---|
| US10125635B2 (en) | 2018-11-13 |
| JP6730031B2 (en) | 2020-07-29 |
| US20160201556A1 (en) | 2016-07-14 |
| EP3043029A1 (en) | 2016-07-13 |
| JP2016130516A (en) | 2016-07-21 |
| EP3043029B1 (en) | 2019-06-19 |
| CN105781625B (en) | 2020-03-31 |
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